ATV3 Factsheet

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The Automated Transfer Vehicle (ATV) is an unmanned automatic vehicle which is put in orbit by the European Ariane 5 launcher. It provides the International Space Station with: pressurized cargo, water, air, nitrogen, oxygen and attitude control propellant.
It also removes waste from the station and re-boosts it to a higher altitude to compensate for the atmospheric drag.

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ATV3 Factsheet

  1. 1. → ATV-3 EDOARDO AMALDIEuropean servicing and logistics vehicleThe Automated Transfer Vehicle (ATV) is an unmanned automatic vehicle which is put in orbit by the European Ariane 5 launcher.It provides the International Space Station with: pressurized cargo, water, air, nitrogen, oxygen and attitude control propellant.It also removes waste from the station and re-boosts it to a higher altitude to compensate for the atmospheric drag. GPS antennas for positioning TDRS antennas for communication S-Band Antenna Attitude control and braking thrusters (28 x 220 N) 2 x visual targets for crew monitoring Ranging Main engine cues (4 x 490 N) 2 x star trackers 4 x solar arrays for generation Multi-Layer of electricity Insulation blanket Russian docking system 4 x optical rendez-vous sensors PROJECT: International Space Station TITLE: Automated DOCUMENT N°: REV. Transfer Vehicle-3 ESA-HSO-COU-023 2.0ERASMUS Centre - Directorate of Human Spaceflight and Operations
  2. 2. 4480 22281 DIMENSIONS: in mmThe Integrated Cargo Carrier (ICC) ATV-3 containers being offloaded in Kourou harbour from the French cargo ship MN Toucan on 25 August 2011
  3. 3. SpecificationsDIMENSIONS THERMAL/ENVIRONMENTAL CONTROLLength: 9,794 mm (probe retracted) Thermal Control: Multi Layer Insulation material, activeLargest diameter: 4,480 mm thermal control using Variable &Solar arrays span: 22,281 mm Constant Conductive Heat Pipes and paintsMASS BUDGET ECLSS: Fire detection, air circulation,Vehicle dry mass: 9,778 kg air temperature monitoringVehicle consumables: 2,261 kgTotal vehicle mass: 12,039 kg ELECTRICAL POWERTotal cargo upload capacity: 7,384 kg Ascent to ISS and de-orbit: 4 Solar panel wings of 4 panels eachMass at launch (max): 20,100 kg and 40 Ah rechargeable batteriesWaste download capacity: 6,495 kg (420 km altitude, Number of arrays: 4 51.6° inclination) Number of panels/array: 4 Generated power: 3,800 W after 6 months in orbitPROPULSION Required power: < 400 W Dormant modeMain propulsion system: 4 x 490 N thrusters supplied by ISS: < 900 W Active mode (Pressurized liquid bi-propellant system) MAIN CONSTRUCTION MATERIALAttitude control system: 28 x 220 N thrusters (Pressurized Pressure shell: Al - 2219 liquid bi-propellant system) Micrometeoroid and Primary bumper: Al-6061-T6Propellant: Monomethyl hydrazine fuel and Debris Protection System: Secondary bumper: Nextel/Kevlar blankets Nitrogen tetroxide oxidizer Internal structure (racks): Al-6061-T6Pressurization: Helium pressurant at 31 MPa Thermal insulation: Goldised Kapton Multi-layer Insulation blanket & aluminised beta clothAVIONICS Solar arrays: Silicium Solar Cells on 4 Carbon Fibre• 2 Failures tolerant architecture Reinforced Plastic Sandwich panels• Equipment Interconnection via multiple redundant MIL-STD-1553B buses MAIN CONTRACTOR• 2 Fault tolerant Computer via voting mechanisms Astrium-Space Transportation, leading a consortium of many• Flight Application Software: 450000 lines of code sub-contractorsCOMMUNICATIONS INFRASTRUCTURETo ground: S-band via TDRS satelliteATV to ISS: S-band antenna via Proximity linkRELATIVE NAVIGATION PROJECT: International• Relative GPS Space Station• Optical rendez-vous sensors TITLE: Automated DOCUMENT N°: REV. Transfer Vehicle-3 ESA-HSO-COU-023 2.0 ATV-3 in preparation at ATV-2 Johannes Kepler approach seen by ESA astronaut the Guiana Space Centre Paolo Nespoli from the International Space Station
  4. 4. Utilisation Relevant DataLAUNCH CONFIGURATION ON ORBIT CONFIGURATIONPayload: 8 racks with 1.25 m3 each Deployed solar arrays, with a total span of 22.3 m,envelope: 1.005 m3 in front of 2 racks that provide electrical power to rechargeable batteriesCargo mass: Dry cargo: 2400 kg for eclipse periods. Automated flight towards the Water: 285 kg International Space Station. Gas (Nitrogen, Oxygen, air, max. 2 gases/flight): 100 kg FLIGHT HARDWARE ISS Refuelling propellant: 860 kg Propulsion and re-boost system (306 kg of fuel, 554 kg of oxidizer) Avionics equipment ISS re-boost and attitude control Guidance navigation and control system propellant: 2959 kg Communications system Total cargo upload capacity: 6604 kg Power generation and storage systemLaunch vehicle: Ariane 5 (300 x 300 km, 51.6° transfer Thermal control system orbit) ATV-3 will be launched with its Russian docking and refuelling system solar panels folded to the body of the spacecraft. Electrical power will be supplied by rechargeable batteries.Launch site: Kourou, French GuianaLaunch date: 9 March 2012 (as of 7 December 2011) Primary Stand-off structure Water and gas tank Refuelling System Propulsion Module (PM) Payload racks Avionics Module (AM) Multi-Layer Insulation blanket Micrometeoroid and orbital debris protection system Illustrations: ESA/D. Ducros Spacecraft subassembly Integrated Cargo Carrier (ICC)http://erasmus.spaceflight.esa.int http://www.esa.int/atv

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